Airplane



Fb. 18, 1930. v. J. BURNELLI AIRPLANE Filed May '7. 1927 2 Sheets-Sheet 4- INVENTOR.

A TTORNEY 7 Feb. 18, 1930. v, J BURNELL] I 1,747,695

AIRPLANE Filed May 1927 2 Sheets-Sheet 2 INVEN TOR.

ATTORNEY Patented Feb. 18, 1930 "UNITED STATES PATENT OFFICE VINCENT J. BURNELLI, OF NEW YORK, N. Y., ASSIGNOR TO THE UPPERCU-BURNELLI CORPORATION, A CORPORATION OF DELAWARE AIRPLANE Application filed May 7, 1927. Serial No. 189,526.

This invention relates to means associated with an airplane fuselage or airfoil .in which the engines are housed, and my improvements are directed to a novel cooling system for the engines, wherein the radiators for the engine cooling water are disposed in the forward part or nose of the fuselage or airfoil to permit the pressure passage of air therethrough, and wherein the air forced through the radiator is guided to flow contactingly over the engine and is facilitated in its flow passage by powerful suction means engendered in the flight of the airplane, side outlets for the flowing air being provided at points rearwardly of the engines, where suction aids the outflow.

Other features and advantages of my said invention will hereinafter appear.

In the drawings Figure 1 is a front elevation of a monoplane of the Remington-Burnelli type embodying my im roved engine cooling system, the side wings Being broken away.

Fig. 2 is a top plan view of the forward portion thereof.

Fig. 3 is a side elevation in which appears only the forward portion of themonoplane. Fig. 4 is a partial top plan view, partly in horizontal section, showing the course of air flowing through a radiator, over an engine and out through a side opening, and

Fig. 5 is an enlarged side sectional view through the fuselage nose and a radiator therein.

Since my improvements engine cooling means have been devised primarily for use in the Remington-Burnelli type of large passenger and freight carrying airplanes where in the fuselage is of aerofoil contour throughout, to comprise a central supporting unit, I have by way of example illustrated said improvements as applied to a monoplane of said type.

In the views let 1 indicate a fuselage of aerofoil contour, having the nose portion 2, in which the engines 3, 3 are housed and disposed one at each side within said nose-.portion; the engine shafts projecting forwardly and respectively carrying the propellers 4, 4. that operate in the same vertical plane.

Fitted in the front of nose portion 2 are radiators 5, 5 arranged side by side, in spaced relation, the width of the fuselage nose portion permitting this. arrangement and thereby enabling so large an area of radiator surface to be exposed, head-on in the direction of flight. The radiators here shown are of the honeycomb type for the passage of cool ing currents of air therethrough, while rearwardly of the radiators I provide guide-ways 6o 6, 6 to direct the flowing air against and over the engines and toward outlets 7, 7 formed in the fuselage sides.

The advantage gained by the aforesaid arrangement and disposition of the radiators is two-fold. In the first place the slip-stream from the propellers, plus the head-on air pressure is forced at high speed through the cellular formation of the radiators, whereby a highly eflicient cooling effect is produced upon the circulatory water, and at the same time head resistance is reduced because of the free passage-way through the radiators; secondly the passage of these large volumes of cooling air over the engines is beneficial in lowering vthe temperature thereof. Further by the provision of the guide means 6, 6 lead-. ing to the rearward outlets 7 7, not only is free delivery of the passing air permitted, but this delivery is accelerated by the powerful suction created at the openings 7, 7 in the flight of the airplane.

Variations within the spirit and scope of my invention are equally comprehended by the foregoing disclosure.

I claim:

1. The combination with an airplane having a supporting airfoil, of separate engines housed within the. forward portion of said airfoil, respectively at opposite sides thereof, and propellers operated by said engines in the same plane, radiators fitted in said forward portion between said engines, and guide means to so direct air flowing through said radiators that streams thereof will pass contactingly over said engines, the sides of said airfoil having outlets disposed rearwardly of the engines, .to permit suction pull to be exerted 'upon the flowing air streams.

2. The combination with an airplane hav- A ing a supporting airfoil, of separate engines housed within the forward portion of said airfoil, respectively at opposite sides thereof, and propellers operated by said engines in the same plane, cooling air inlet means fitted in said forward portion between said engines, and guide means to so direct air flowing through said inlet means that streams thereof will pass contactingly over said en- 10 gines, the sides of said airfoil having outlets disposed rearwardly of the engines, to permit suction pull to be exerted upon the flowing air-streams.

New York, March 6th, 1927.

15 VINCENT J. BURNELLI. 

